A two-dlnensional motor was designed, fabricated, and tested to establish improved techniques for measuring the dynamic characteristics of the combustion mechanism in an operating thrust chamber. The criteria on which the design of the .TiOtor was based; the experimental equipment, and the tests conducted are described. The methods by which this nctor can be used to investigate stable and unstable cccibustion are discussed and the correlations necessary to relate the observed phenomena to the behavior of full-scale rocket engines are indicated.

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A review of current technology applied to sensors for the measurement of speed, temperature, and pressure in gas turbine engines. The use of suitable materials and designs to overcome the hostile environments is discussed. The desirability of obtaining a simple interface with control systems is considered.